Experiments on transitional shock wave--boundary layer interactions at Mach 5

Erdem, Erinc; Kontis, Konstantinos; Johnstone, Eleanor C.; Murray, N.; Steelant, Johan

doi:10.1007/s00348-013-1598-z

Cited by 32 publications

(12 citation statements)

References 26 publications

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“…However for lower contraction ratios a shrunk separation region has been obtained. There are many more research papers (Murugan et al 2015;Erdem et al 2013) that dealing with intake design available in the open literature. In all such studies boundary layer separation resulting from the interaction of cowl lip shock with the boundary layer over the ramp surface/isolator wall has been observed to be a key phenomenon that seize the performance of the intake section.…”

Section: Introductionmentioning

confidence: 99%

Alterations of Cowl Lip for the Improvement of Supersonic-Intake Performance

John

Senthilkumar

2018

JAFM

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This paper discusses the performance enhancement of supersonic air intake model through the implementation of blunted leading edge to the cowl lip section of the model. A supersonic air intake model with sharp cowl leading edge is initially considered to numerically investigate its performance. Mach 3, supersonic intake flow through the base model has been simulated using commercial CFD package Ansys Fluent-15. Comparison of numerical predictions and experimental measurements is presented to demonstrate the correctness and accuracy of numerical frame work followed in the present study. Higher order spatial accuracy of the solver along with suitably refined mesh helped in accurate capturing of the flow field. Modification to the cowl lip is proposed as an effective method to improve the performance of the supersonic air intake. Two different blunted cowl leading edge geometries were investigated to identify the possible enhancement in performance parameters. Improvement in mass capture and combustion stability attained through the use of forward shifted blunt cowl leading edge is presented. It is also revealed through the present study that the blunt cowl leading edge can reduce the intensity of shock wave boundary layer interaction occurring at the isolator entry section. Deviation in total pressure recovery and flow distortion observed with different supersonic air intake models are also discussed with reasons for the same. This study demonstrates the scope of overall improvement in scramjet engine performance through the use of suitably positioned blunt cowl leading edge.

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Section: Introductionmentioning

confidence: 99%

Alterations of Cowl Lip for the Improvement of Supersonic-Intake Performance

John

Senthilkumar

2018

JAFM

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“…In the recent work of Erdem et al (2013), PIV measurements were performed (among other techniques) on laminar and transitional SWBLI at Mach 5. The impinging shock wave (7° flow deflection angle) separates the incoming boundary layer, and transition is recorded near the end of the separation bubble.…”

Section: Introductionmentioning

confidence: 99%

High-resolution PIV measurements of a transitional shock wave-boundary layer interaction

Giepman

Schrijer

Oudheusden

2014

44th AIAA Fluid Dynamics Conference

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“…Finally, it is noticed that two different definitions of the characteristic time scale of the flow field are used in experiments of CTBL, either τ f = δ/U ∞ (Ganapathisubramani et al 2006;Lapsa & Dahm 2011;Brooks et al 2018;Peltier et al 2018) or τ f = 10δ/U ∞ (Erdem et al 2013;Neeb, Saile & Gülhan 2018;Williams et al 2018), respectively. Here δ is the boundary layer thickness at the position of interest, and U ∞ is the free-stream velocity.…”

Section: Discussionmentioning

confidence: 99%